1FMTD/VSSC, ISRO, Thiruvananthapuram-695 022, India.
2Department of Aerospace Engineering, Indian Institute of Space Science and Technology, ISRO, Thiruvananthapuram-695 022, India.
3Department of Mechanical Engineering, Indian Institute of Technology Bombay, India, 440076.
*Corresponding author
A numerical simulation of film cooling for reentry module is presented. The developed numerical procedure is based on AUSM+-UP scheme using higher order accurate reconstruction method. Numerical simulation of film cooling provides vital information required for design of effective cooling system such as number of counter flow injectors, their dimensions and locations, injection pressure and temperature, mass flow rate required etc. The numerical code has been successfully validated using standard experimental data for counter flow injection. Analysis has been carried out for a simple axisymmetric reentry module with and without film cooling, for a free stream Mach number of 8.0. The predicted adiabatic wall temperatures were compared for both the cases. Film cooling is found to be effective for this configuration and injected coolant remains confined to the boundary layer formed by the free stream from nose tip to the aft end of the module.
Hypersonic flow, reentry module, counter flow jet, film cooling, Finite Volume Method, AUSM+-UP schemes, higher order reconstruction
